US9260859B2 - Wall structure with noise damping insulation properties and gas turbine with such a wall structure - Google Patents

Wall structure with noise damping insulation properties and gas turbine with such a wall structure Download PDF

Info

Publication number
US9260859B2
US9260859B2 US13/604,373 US201213604373A US9260859B2 US 9260859 B2 US9260859 B2 US 9260859B2 US 201213604373 A US201213604373 A US 201213604373A US 9260859 B2 US9260859 B2 US 9260859B2
Authority
US
United States
Prior art keywords
beams
perforated sheets
noise damping
gas turbine
outer sheet
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related, expires
Application number
US13/604,373
Other languages
English (en)
Other versions
US20130071231A1 (en
Inventor
Mladen Matan
Marc RAUCH
Eduard BRÜHWILER
Antun Svilicic
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ansaldo Energia IP UK Ltd
Original Assignee
Alstom Technology AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Assigned to ALSTOM TECHNOLOGY LTD reassignment ALSTOM TECHNOLOGY LTD ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: MATAN, MLADEN, Svilicic, Antun, BRUHWILER, EDUARD, RAUCH, MARC
Publication of US20130071231A1 publication Critical patent/US20130071231A1/en
Application granted granted Critical
Publication of US9260859B2 publication Critical patent/US9260859B2/en
Assigned to GENERAL ELECTRIC TECHNOLOGY GMBH reassignment GENERAL ELECTRIC TECHNOLOGY GMBH CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: ALSTOM TECHNOLOGY LTD
Assigned to ANSALDO ENERGIA IP UK LIMITED reassignment ANSALDO ENERGIA IP UK LIMITED ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: GENERAL ELECTRIC TECHNOLOGY GMBH
Expired - Fee Related legal-status Critical Current
Adjusted expiration legal-status Critical

Links

Images

Classifications

    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04B—GENERAL BUILDING CONSTRUCTIONS; WALLS, e.g. PARTITIONS; ROOFS; FLOORS; CEILINGS; INSULATION OR OTHER PROTECTION OF BUILDINGS
    • E04B1/00—Constructions in general; Structures which are not restricted either to walls, e.g. partitions, or floors or ceilings or roofs
    • E04B1/62—Insulation or other protection; Elements or use of specified material therefor
    • E04B1/74—Heat, sound or noise insulation, absorption, or reflection; Other building methods affording favourable thermal or acoustical conditions, e.g. accumulating of heat within walls
    • E04B1/82—Heat, sound or noise insulation, absorption, or reflection; Other building methods affording favourable thermal or acoustical conditions, e.g. accumulating of heat within walls specifically with respect to sound only
    • E04B1/84—Sound-absorbing elements
    • E—FIXED CONSTRUCTIONS
    • E04—BUILDING
    • E04B—GENERAL BUILDING CONSTRUCTIONS; WALLS, e.g. PARTITIONS; ROOFS; FLOORS; CEILINGS; INSULATION OR OTHER PROTECTION OF BUILDINGS
    • E04B2/00—Walls, e.g. partitions, for buildings; Wall construction with regard to insulation; Connections specially adapted to walls
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/24—Heat or noise insulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/663—Sound attenuation
    • F04D29/664—Sound attenuation by means of sound absorbing material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/171—Steel alloys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/612—Foam

Definitions

  • the present invention relates to the technology of gas turbines. It refers to a wall structure with noise damping insulation properties, especially for an air intake manifold of a gas turbine.
  • Gas turbines use ambient air as combustion air for the combustion of fuel to generate hot gas, which drives a turbine.
  • the exemplary gas turbine 10 of FIG. 1 is equipped with sequential combustion. It comprises a compressor 12 for compressing the combustion air, a first combustor 13 , a first turbine 14 , a second combustor 15 and a second turbine 16 .
  • the ambient air to be compressed by the compressor 12 enters the gas turbine through an air intake 11 .
  • FIG. 1 shows the bare gas turbine 10 .
  • the ambient air which is compressed by the compressor 12 , usually has to be filtered and in some cases mixed with water by means of a fogging device, before being introduced into the compressor through the air duct, air intake manifold 17 , and the air intake 11 .
  • an air intake manifold 17 as shown in FIG. 2 , is used to guide the air from the entrance of a gas turbine plant to the air intake 11 of gas turbine 10 .
  • the air intake manifold 17 of FIG. 2 is made up of several walls 18 , which enclose an inner space with an inlet opening 19 and an outlet opening 20 , the outlet opening 20 being adapted to the air intake 11 of the gas turbine 10 .
  • the air intake manifold 17 has a wall structure 21 , which serves several purposes:
  • the air intake manifold 17 of FIG. 2 has a wall structure 21 a part of which is shown in FIG. 3 .
  • a frame of L beams 22 which is reinforced with crossing ribs 23 , supports from the outside an outer sheet 24 , which separates the inner space (on the left of outer sheet 24 in FIG. 3 ) of the air intake manifold 17 from the outside (on the right of outer sheet 24 FIG. 3 ).
  • a noise damping insulation is provided on and assembled from the inner side of the outer sheet 24 .
  • Insulation ribs 26 made of stainless steel (X6CrNiTi18-10 or similar) are welded on the outer sheet 24 forming square frames (see also FIG. 2 ).
  • Each frame is filled with a noise damping insulation material 25 made for example of melamine foam with a thickness of 45 mm.
  • the noise damping insulation material 25 or melamine foam is covered with 3 mm thick perforated sheets 27 made of stainless steel.
  • Fixation plates 28 are welded on the insulation ribs to keep the perforated sheets 27 in place.
  • An example of an air intake manifold and wall structure is disclosed in document US 2008/0202848 A1.
  • the present disclosure is directed to a wall structure with noise damping insulation properties for an air intake manifold of a gas turbine.
  • the wall structure includes a first structure that mechanically supports an outer sheet, which separates spaces on both sides of the wall in an airtight manner, and further includes a second structure that establishes noise damping insulation between the spaces on both sides of the wall.
  • the second structure is secured to the first structure and the second structure is integrated in the first structure.
  • the present disclosure is also directed to a gas turbine, which includes the above wall structure.
  • FIG. 1 shows a perspective view of a type GT26 stationary gas turbine with sequential combustion
  • FIG. 2 shows a perspective view of a prior art air intake manifold for the turbine of FIG. 1 ;
  • FIG. 3 shows a cross-section of the wall structure of the air intake manifold of FIG. 2 ;
  • FIG. 4 shows a cross-section of the wall structure of an air intake manifold according to an embodiment of the invention
  • FIG. 5 shows a front view from the interior on the wall of a partially assembled air intake manifold (without melamine foam and perforated plates) according to an embodiment of the invention.
  • FIG. 6 shows a section of the perforated sheet used in a wall structure according to FIG. 4 .
  • the wall structure of the invention comprises first means for mechanically supporting an outer sheet, which separates the spaces on both sides of the wall, e.g. the surroundings and the air duct of an air intake manifold, in an airtight manner, and further comprises second means for establishing noise damping insulation between the spaces on both sides of the wall, whereby said second means is secured to said first means, and said second means is integrated in said first means.
  • the first means comprises a plurality of I-beams, which are arranged in a common plane with their webs oriented perpendicular to said common plane, the outer sheet is secured to a first one of the flanges of the I-beams, and said second means comprises the space between the I-beams being filled with a noise damping insulation material.
  • the noise damping insulation material is enclosed between said outer sheet and perforated sheets, which are secured to a second one of the flanges of the I-beams.
  • the I-beams and the outer sheet are made of a carbon steel, and the perforated sheets are made of stainless steel.
  • intermediate strips of stainless steel are provided between the perforated sheets and the second one of the flanges ( 31 b ) of the I-beams.
  • the supporting structure with the I-beams is reinforced by providing intermediate beams between the I-beams, which intermediate beams support said perforated sheets.
  • the intermediate beams are L-beams, and strips of stainless steel are provided between the perforated sheets and the L-beams.
  • the perforated sheets are welded on the I-beams or intermediate strips, respectively, and the perforated sheets are provided with cut-outs being used for said welding.
  • the perforated sheets are free of holes in a border area around said cut-outs. They can also be free of holes on their outer borders.
  • the noise damping insulation material is a foam, especially on the basis of a melamine resin.
  • the I-beams are of a standard IPB 100 type.
  • the outer sheet has a thickness of 4 mm, the I-beams are corrosion protected, and the perforated sheets have a thickness of the 3 mm.
  • the invention further provides a gas turbine comprising a compressor, which is supplied with air by means of an air intake manifold where the walls of the air intake manifold have a wall structure according to the invention.
  • the invention proposes to measures, namely the integration of the noise damping insulation in the wall structure (without insulation ribs), and the waiving of several small parts welded in the flow channel.
  • the new wall structure 30 is composed of I-beams 31 (e.g. of the IPB 100 type), which are used as main structural elements.
  • the I-beams 31 which are arranged in a common plane with their webs 31 a oriented perpendicular to said common plane, support (with their inner flanges 31 b ) perforated sheets 36 on the inside of the structure.
  • the frame 37 with its I-beams 31 is reinforced with additional L-beams 33 .
  • the L beams 33 also serve to support said perforated sheets 36 , can support the insulation against movement and, if required can support the outer sheet 32 .
  • the outer sides or outer flanges 31 b of the I-beams 31 are covered with a 4 mm thick outer sheet 32 of carbon steel to ensure air tightness.
  • Stainless steel intermediate strips 34 and 35 are welded on the inner sides or flanges 31 b of the I-beams 31 (i.e. in the flow channel) and L-beams 33 .
  • the space between the I-beams 31 and L-beams 33 is filled with 105 mm thick melamine foam as noise damping insulation material 25 .
  • the melamine foam is then covered with 3 mm thick stainless steel perforated sheets 36 (see FIG. 6 ).
  • the perforated sheets 36 are welded on the stainless steel intermediate strips 34 and 35 .
  • the provision of the stainless steel intermediate strips 34 , 35 allows the application of cheap mild steel for the I-beams 31 (and L-beams 33 ).
  • the stainless steel perforated sheets 36 are then welded to the stainless steel intermediate strips 34 and 35 .
  • cut-outs are only indicated for welding the I-beams 35 . Similar cut outs can also be provided for welding the L-beams 33 .
  • the I-beams 31 of the invention have the advantage that they are stiff during welding. This is not the case for the insulation ribs 26 of the prior art, when the perforated sheets 27 and fixation plates 28 are welded to them.
  • the perforated sheets 36 are preferably made from a large sheet, as shown in FIG. 6 .
  • cut-outs 38 are provided.
  • the perforated sheets 36 are preferably free of holes 40 in a border area 39 around said cut-outs 38 so that the cut-outs 38 have straight borders being advantageous for the welding process.
  • the perforated sheets 36 are preferably also free of holes 40 in for the outer border area of the perforated sheets 36 .
  • the melamine foam 25 is flexible and can be introduced between the I-beams 31 and L-Beams 33 without problems.
  • noise damping insulation material e.g. melamine foam

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Architecture (AREA)
  • Acoustics & Sound (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Electromagnetism (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Building Environments (AREA)
  • Devices Affording Protection Of Roads Or Walls For Sound Insulation (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
US13/604,373 2011-09-12 2012-09-05 Wall structure with noise damping insulation properties and gas turbine with such a wall structure Expired - Fee Related US9260859B2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP11180934 2011-09-12
EP11180934 2011-09-12
EP11180934.9 2011-09-12

Publications (2)

Publication Number Publication Date
US20130071231A1 US20130071231A1 (en) 2013-03-21
US9260859B2 true US9260859B2 (en) 2016-02-16

Family

ID=46727155

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/604,373 Expired - Fee Related US9260859B2 (en) 2011-09-12 2012-09-05 Wall structure with noise damping insulation properties and gas turbine with such a wall structure

Country Status (3)

Country Link
US (1) US9260859B2 (de)
EP (1) EP2568144B1 (de)
RU (1) RU2545266C2 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170022903A1 (en) * 2015-07-21 2017-01-26 The Boeing Company Sound attenuation apparatus and method
US9587563B2 (en) 2015-07-21 2017-03-07 The Boeing Company Sound attenuation apparatus and method
US9714630B2 (en) * 2015-10-07 2017-07-25 General Electric Company Noise baffle for a rotary machine and method of making same
US10344774B2 (en) * 2015-09-29 2019-07-09 Rolls-Royce Plc Casing for a gas turbine engine and a method of manufacturing such a casing

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108843452B (zh) * 2018-06-14 2021-10-26 哈尔滨工业大学（威海） 一种船舶用燃气轮机箱装体

Citations (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4452335A (en) * 1982-05-03 1984-06-05 United Technologies Corporation Sound absorbing structure for a gas turbine engine
US4753319A (en) * 1985-10-16 1988-06-28 Nuovopignone S.P.A. Exhaust silencer for high-power gas turbines
US4944362A (en) * 1988-11-25 1990-07-31 General Electric Company Closed cavity noise suppressor
US5594216A (en) 1994-11-29 1997-01-14 Lockheed Missiles & Space Co., Inc. Jet engine sound-insulation structure
EP0819842A1 (de) 1996-07-15 1998-01-21 Siemens Aktiengesellschaft Vorrichtung zum Befestigen eines Abdeckbleches im Rauchgaskanal einer Gasturbine
US6182787B1 (en) 1999-01-12 2001-02-06 General Electric Company Rigid sandwich panel acoustic treatment
US6439340B1 (en) 2000-11-17 2002-08-27 Astech Manufacturing, Inc. Acoustically treated structurally reinforced sound absorbing panel
US20030072648A1 (en) * 2001-05-30 2003-04-17 Han Ming Hui Outlet silencer structures for turbine
US20040045765A1 (en) * 2002-09-10 2004-03-11 Alain Porte Tubular acoustic attenuation piece for an aircraft jet engine air intake
RU2241843C1 (ru) 2003-07-14 2004-12-10 Открытое акционерное общество Научно-производственное объединение "Искра" Звукопоглощающий кожух газотурбинной установки
EP1657374A2 (de) 2004-11-12 2006-05-17 General Electric Company Wärme- und schall- dämmendes Gehäuse
US20080202848A1 (en) * 2005-08-08 2008-08-28 Alstom Technology Ltd Sound absorber for gas turbine installations
FR2934641A1 (fr) 2008-07-30 2010-02-05 Aircelle Sa Panneau d'attenuation acoustique pour nacelle de moteur d'aeronef
EP2192289A1 (de) 2007-09-13 2010-06-02 Alphatech CO., LTD. Ansaugschalldämpfer für eine gasturbine
FR2940360A1 (fr) 2008-12-22 2010-06-25 Aircelle Sa Panneau d'attenuation acoustique pour nacelle de moteur d'aeronef,structure d'entree d'air et structure interne fixe incorporant ledit panneau
US7798285B2 (en) * 2008-11-14 2010-09-21 Rohr, Inc. Acoustic barrel for aircraft engine nacelle including crack and delamination stoppers
US20110133025A1 (en) * 2008-07-30 2011-06-09 Aircelle Acoustic attenuation panel for aircraft for engine nacelle

Patent Citations (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4452335A (en) * 1982-05-03 1984-06-05 United Technologies Corporation Sound absorbing structure for a gas turbine engine
US4753319A (en) * 1985-10-16 1988-06-28 Nuovopignone S.P.A. Exhaust silencer for high-power gas turbines
US4944362A (en) * 1988-11-25 1990-07-31 General Electric Company Closed cavity noise suppressor
US5594216A (en) 1994-11-29 1997-01-14 Lockheed Missiles & Space Co., Inc. Jet engine sound-insulation structure
EP0819842A1 (de) 1996-07-15 1998-01-21 Siemens Aktiengesellschaft Vorrichtung zum Befestigen eines Abdeckbleches im Rauchgaskanal einer Gasturbine
US6182787B1 (en) 1999-01-12 2001-02-06 General Electric Company Rigid sandwich panel acoustic treatment
US6439340B1 (en) 2000-11-17 2002-08-27 Astech Manufacturing, Inc. Acoustically treated structurally reinforced sound absorbing panel
US20030072648A1 (en) * 2001-05-30 2003-04-17 Han Ming Hui Outlet silencer structures for turbine
US20040045765A1 (en) * 2002-09-10 2004-03-11 Alain Porte Tubular acoustic attenuation piece for an aircraft jet engine air intake
RU2241843C1 (ru) 2003-07-14 2004-12-10 Открытое акционерное общество Научно-производственное объединение "Искра" Звукопоглощающий кожух газотурбинной установки
EP1657374A2 (de) 2004-11-12 2006-05-17 General Electric Company Wärme- und schall- dämmendes Gehäuse
US20080202848A1 (en) * 2005-08-08 2008-08-28 Alstom Technology Ltd Sound absorber for gas turbine installations
US7832524B2 (en) 2005-08-08 2010-11-16 Alstom Technology Ltd Sound absorber for gas turbine installations
EP2192289A1 (de) 2007-09-13 2010-06-02 Alphatech CO., LTD. Ansaugschalldämpfer für eine gasturbine
FR2934641A1 (fr) 2008-07-30 2010-02-05 Aircelle Sa Panneau d'attenuation acoustique pour nacelle de moteur d'aeronef
US20110133025A1 (en) * 2008-07-30 2011-06-09 Aircelle Acoustic attenuation panel for aircraft for engine nacelle
US7798285B2 (en) * 2008-11-14 2010-09-21 Rohr, Inc. Acoustic barrel for aircraft engine nacelle including crack and delamination stoppers
FR2940360A1 (fr) 2008-12-22 2010-06-25 Aircelle Sa Panneau d'attenuation acoustique pour nacelle de moteur d'aeronef,structure d'entree d'air et structure interne fixe incorporant ledit panneau

Non-Patent Citations (5)

* Cited by examiner, † Cited by third party
Title
Decision of Grant issued Oct. 20, 2014 by the Russian Patent Office in corresponding Russian Patent Application No. 2012138961, and an English translation thereof (10 pages).
European Search Report, Jan. 26, 2012, 8 pp.
NA 021-00-21-06 UA (Responsible Committee), DIN 1025, Nov. 1995, Germany. *
Office Action issued on May 15, 2014, by the Russian Patent Office in corresponding Russian Patent Application No. 2012138961, and an English Translation of the Office Action. (9 pages).
Steel and Iron Standards Committee, Germany, DIN 1025-2, Nov. 1995, pp. 1-3. *

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170022903A1 (en) * 2015-07-21 2017-01-26 The Boeing Company Sound attenuation apparatus and method
US9587563B2 (en) 2015-07-21 2017-03-07 The Boeing Company Sound attenuation apparatus and method
US9771868B2 (en) * 2015-07-21 2017-09-26 The Boeing Company Sound attenuation apparatus and method
US9963238B2 (en) 2015-07-21 2018-05-08 The Boeing Company Sound attenuation apparatus and method
US10344774B2 (en) * 2015-09-29 2019-07-09 Rolls-Royce Plc Casing for a gas turbine engine and a method of manufacturing such a casing
US9714630B2 (en) * 2015-10-07 2017-07-25 General Electric Company Noise baffle for a rotary machine and method of making same

Also Published As

Publication number Publication date
EP2568144A3 (de) 2017-03-01
RU2012138961A (ru) 2014-04-27
RU2545266C2 (ru) 2015-03-27
EP2568144B1 (de) 2019-11-06
US20130071231A1 (en) 2013-03-21
EP2568144A2 (de) 2013-03-13

Similar Documents

Publication Publication Date Title
US9260859B2 (en) Wall structure with noise damping insulation properties and gas turbine with such a wall structure
US8689932B2 (en) On-base enclosure
US9546582B1 (en) Silencer panel having sections and related silencer duct
EP3330458A1 (de) Trägerelement, form zum setzen von beton und verfahren zur konstruktion einer betonstruktur
US9109800B2 (en) Quick disengaging field joint for exhaust system components of gas turbine engines
US9915066B2 (en) Sound absorbing panel and soundproof wall equipment
US20070278035A1 (en) Thermal-acoustic enclosure
US10971127B2 (en) Enclosure for a gas turbine engine
US8556028B1 (en) Acoustic module for enclosure panel
JP6271182B2 (ja) 消音板ユニットおよびこれを用いたセル形消音器ならびに消音設備
US10900224B2 (en) Prefabricated demising wall with external conduit engagement features
JP2015086875A (ja) ガスタービンエンクロージャ
JP5614624B2 (ja) 爆風圧低減構造体
US11591954B2 (en) Enclosure segments for forming an enclosure for an engine generator set
JP6375339B2 (ja) 吸音パネル及び防音対策設備
US9389001B2 (en) Boiler, and a silencer for a flue gas duct in a boiler
EP3144503B1 (de) Schalldämpfer-panel und system mit perforierter kunststoffseitenwand
JP2009139042A (ja) 軽量不燃性ダクト
US20130225066A1 (en) Protective cover for a ventilation opening
KR101836098B1 (ko) 방화/방폭벽의 단열재 시공방법
JP4772393B2 (ja) 船舶用内部仕切り
JP6649119B2 (ja) 排気ガス消音器、ガスタービン設備、及び原子力プラント
JP2008223410A (ja) 吸音パネル
SE518302C2 (sv) Luckanordning
Glass et al. Ground Runup Noise Suppression Program. Part 3. Dry Suppressor Technology Base.

Legal Events

Date Code Title Description
AS Assignment

Owner name: ALSTOM TECHNOLOGY LTD, SWITZERLAND

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:MATAN, MLADEN;RAUCH, MARC;BRUHWILER, EDUARD;AND OTHERS;SIGNING DATES FROM 20121109 TO 20121116;REEL/FRAME:029412/0796

FEPP Fee payment procedure

Free format text: PAYOR NUMBER ASSIGNED (ORIGINAL EVENT CODE: ASPN); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

STCF Information on status: patent grant

Free format text: PATENTED CASE

AS Assignment

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, SWITZERLAND

Free format text: CHANGE OF NAME;ASSIGNOR:ALSTOM TECHNOLOGY LTD;REEL/FRAME:038216/0193

Effective date: 20151102

AS Assignment

Owner name: ANSALDO ENERGIA IP UK LIMITED, GREAT BRITAIN

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:GENERAL ELECTRIC TECHNOLOGY GMBH;REEL/FRAME:041731/0626

Effective date: 20170109

FEPP Fee payment procedure

Free format text: MAINTENANCE FEE REMINDER MAILED (ORIGINAL EVENT CODE: REM.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

LAPS Lapse for failure to pay maintenance fees

Free format text: PATENT EXPIRED FOR FAILURE TO PAY MAINTENANCE FEES (ORIGINAL EVENT CODE: EXP.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY

STCH Information on status: patent discontinuation

Free format text: PATENT EXPIRED DUE TO NONPAYMENT OF MAINTENANCE FEES UNDER 37 CFR 1.362

FP Lapsed due to failure to pay maintenance fee

Effective date: 20200216